A new optimal guidance law(OPG)for air-to-air missiles, based on the design concept of decreasing the acceleration requirement commanded in the final phase of engagement, is presented. The closed-form solution of the OPG is derived analytically from the time-varying linear state equations composed of the line-of-sight angle and line-of-sight rate. The optimal proportional navigation law and augmented proportional navigation law, where both the navigation constants are 3, have been proven to be simplified versions of the OPG.
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